AD 2011-03-01 Airworthiness Directives; Pratt & Whitney JT8D-7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR Series Turbofan Engines

This AD applies to Pratt & Whitney (PW) JT8D-7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan engines. These engines are installed on, but not limited to, Boeing 727 and 737 series, and McDonnell Douglas DC-9 series airplanes.

You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. (f) Within the next 30 days after the effective date of this AD, (1) revise the Time Limits Section (TLS) of the manufacturer's engine manual, part number 481672, as appropriate for PW JT8D-7, -7A, -7B, -9, -9A, -11, -15, -15A, -17, -17A, -17R, and -17AR series turbofan engines, and (2) for air carriers, revise the approved mandatory inspections section of the continuous airworthiness maintenance program, by adding the following: “Critical Life Limited Part Inspection A. Inspection Requirements: (1) This section has the definitions for individual engine piece-parts and the inspection procedures which are necessary when these parts are removed from the engine. (2) It is necessary to do the inspection procedures of the piece-parts in paragraph B when: (a) The part is removed from the engine and disassembled to the level specified in paragraph B and (b) The part has accumulated more than 100 cycles since the last piece-part inspection, provided that the part was not damaged or related to the cause for its removal from the engine. (3) The inspections specified in this paragraph do not replace or make not necessary other recommended inspections for these parts or other parts. B. Parts Requiring Inspection: Note: Piece-part is defined as any of the listed parts with all the blades removed.   Description Section Inspection No. Hub (Disk), 1st Stage Compressor: * Hub Detail—All P/Ns 72-33-31 -03, -04, -05, -06 * Hub Assembly—All P/Ns 72-33-31 -03, -04, -05, -06 2nd Stage Compressor: Disk—All P/Ns 72-33-33 -02, -03 Disk Assembly—All P/Ns 72-33-33 -02, -03 Disk, 13th Stage Compressor—All P/Ns 72-36-47 -02 HP Turbine Disk, First Stage w/integral Shaft—All P/Ns 72-52-04 -03 HP Turbine, First Stage, w/separable Shaft: Rotor Assembly—All P/Ns 72-52-02 -04 Disk—All P/Ns 72-52-02 -03 Disk, 2nd Stage Turbine—All P/Ns 72-53-16 -02 * Disk, 3rd Stage Turbine—All P/Ns 72-53-17 -02, -03 * Disk (Separable), 4th Stage Turbine—All P/Ns 72-53-15 -02, -03 Disk (Integral Disk/Hub), 4th Stage Turbine—All P/Ns 72-53-18 -02” (g) The parts that have an Engine Manual Inspection Task and or Sub Task Number reference updated in the table of this AD are identified by an asterisk (*) that precedes the part nomenclature. (h) Except as provided in paragraph (i) of this AD and, notwithstanding contrary provisions in section 43.16 of the Federal Aviation Regulations (14 CFR 43.16), these mandatory inspections shall be performed only in accordance with the TLS of the manufacturer's engine manual. Alternative Methods of Compliance (AMOC) (i) You must perform these mandatory inspections using the TLS of the manufacturer's engine manual unless you receive approval to use an AMOC under paragraph (j) of this AD. Section 43.16 of the Federal Aviation Regulations (14 CFR 43.16) may not be used to approve alternative methods of compliance or adjustments to the times in which these inspections must be performed. (j) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Maintaining Records of the Mandatory Inspections (k) You have met the requirements of this AD when you revise the TLS of the manufacturer's engine manual as specified in paragraph (f) of this AD. For air carriers operating under part 121 of the Federal Aviation Regulations (14 CFR part 121), you have met the requirements of this AD when you modify your continuous airworthiness maintenance plan to reflect those changes. You do not need to record each piece-part inspection as compliance to this AD, but you must maintain records of those inspections according to the regulations governing your operation. For air carriers operating under part 121, you may use either the system established to comply with section 121.369 or an alternative accepted by your principal maintenance inspector if that alternative: (1) Includes a method for preserving and retrieving the records of the inspections resulting from this AD; and (2) Meets the requirements of section 121.369(c); and (3) Maintains the records either indefinitely or until the work is repeated. (l) These record keeping requirements apply only to the records used to document the mandatory inspections required as a result of revising the TLS of the manufacturer's engine manual as specified in paragraph (f) of this AD. These record keeping requirements do not alter or amend the record keeping requirements for any other AD or regulatory requirement. Related Information (m) For more information about this AD, contact Ian Dargin, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone (781) 238-7178, fax (781) 238-7199; e-mail: ian.dargin@faa.gov. Issued in Burlington, Massachusetts, on January 24, 2011. Thomas A. Boudreau, Acting Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2011-1869 Filed 1-27-11; 8:45 am] BILLING CODE 4910-13-P

This AD results from the need to require enhanced inspection of selected critical life-limited parts of PW JT8D series turbofan engines. We are issuing this AD to prevent critical life-limited rotating engine part failure, which could result in an uncontained engine failure and damage to the airplane.